FR3129181A1 - Nozzle element for a turbomachine - Google Patents
Nozzle element for a turbomachine Download PDFInfo
- Publication number
- FR3129181A1 FR3129181A1 FR2112225A FR2112225A FR3129181A1 FR 3129181 A1 FR3129181 A1 FR 3129181A1 FR 2112225 A FR2112225 A FR 2112225A FR 2112225 A FR2112225 A FR 2112225A FR 3129181 A1 FR3129181 A1 FR 3129181A1
- Authority
- FR
- France
- Prior art keywords
- track
- conductive
- nozzle
- turbomachine
- conductive track
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
- 239000000463 material Substances 0.000 claims abstract description 8
- 230000002093 peripheral effect Effects 0.000 claims abstract description 6
- 238000000151 deposition Methods 0.000 claims description 3
- 238000000034 method Methods 0.000 claims description 3
- 239000000919 ceramic Substances 0.000 claims description 2
- 239000002131 composite material Substances 0.000 claims description 2
- 238000004519 manufacturing process Methods 0.000 claims description 2
- 239000011159 matrix material Substances 0.000 claims description 2
- 239000011153 ceramic matrix composite Substances 0.000 abstract description 2
- 239000011241 protective layer Substances 0.000 description 4
- 238000011144 upstream manufacturing Methods 0.000 description 4
- 229910002481 CuNiMn Inorganic materials 0.000 description 3
- 229910019017 PtRh Inorganic materials 0.000 description 3
- VNNRSPGTAMTISX-UHFFFAOYSA-N chromium nickel Chemical compound [Cr].[Ni] VNNRSPGTAMTISX-UHFFFAOYSA-N 0.000 description 2
- 239000007789 gas Substances 0.000 description 2
- 238000007373 indentation Methods 0.000 description 2
- 239000011859 microparticle Substances 0.000 description 2
- 239000002105 nanoparticle Substances 0.000 description 2
- 229910001120 nichrome Inorganic materials 0.000 description 2
- 229910052697 platinum Inorganic materials 0.000 description 2
- 238000007650 screen-printing Methods 0.000 description 2
- 229910052719 titanium Inorganic materials 0.000 description 2
- 210000003462 vein Anatomy 0.000 description 2
- 239000000443 aerosol Substances 0.000 description 1
- 239000011230 binding agent Substances 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 230000008021 deposition Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000004927 fusion Effects 0.000 description 1
- 239000011521 glass Substances 0.000 description 1
- 239000002241 glass-ceramic Substances 0.000 description 1
- 230000008018 melting Effects 0.000 description 1
- 238000002844 melting Methods 0.000 description 1
- 239000002245 particle Substances 0.000 description 1
- 238000007639 printing Methods 0.000 description 1
- 229910052709 silver Inorganic materials 0.000 description 1
- 239000004332 silver Substances 0.000 description 1
- 239000002904 solvent Substances 0.000 description 1
- 239000007921 spray Substances 0.000 description 1
- 239000000725 suspension Substances 0.000 description 1
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/04—Mounting of an exhaust cone in the jet pipe
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
- B64D33/04—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of exhaust outlets or jet pipes
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D45/00—Aircraft indicators or protectors not otherwise provided for
- B64D45/02—Lightning protectors; Static dischargers
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/78—Other construction of jet pipes
- F02K1/82—Jet pipe walls, e.g. liners
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/78—Other construction of jet pipes
- F02K1/82—Jet pipe walls, e.g. liners
- F02K1/827—Sound absorbing structures or liners
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2230/00—Manufacture
- F05D2230/30—Manufacture with deposition of material
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2230/00—Manufacture
- F05D2230/30—Manufacture with deposition of material
- F05D2230/31—Layer deposition
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/96—Preventing, counteracting or reducing vibration or noise
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/96—Preventing, counteracting or reducing vibration or noise
- F05D2260/963—Preventing, counteracting or reducing vibration or noise by Helmholtz resonators
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2300/00—Materials; Properties thereof
- F05D2300/10—Metals, alloys or intermetallic compounds
- F05D2300/13—Refractory metals, i.e. Ti, V, Cr, Zr, Nb, Mo, Hf, Ta, W
- F05D2300/132—Chromium
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2300/00—Materials; Properties thereof
- F05D2300/10—Metals, alloys or intermetallic compounds
- F05D2300/13—Refractory metals, i.e. Ti, V, Cr, Zr, Nb, Mo, Hf, Ta, W
- F05D2300/133—Titanium
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2300/00—Materials; Properties thereof
- F05D2300/10—Metals, alloys or intermetallic compounds
- F05D2300/14—Noble metals, i.e. Ag, Au, platinum group metals
- F05D2300/141—Silver
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2300/00—Materials; Properties thereof
- F05D2300/10—Metals, alloys or intermetallic compounds
- F05D2300/14—Noble metals, i.e. Ag, Au, platinum group metals
- F05D2300/143—Platinum group metals, i.e. Os, Ir, Pt, Ru, Rh, Pd
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2300/00—Materials; Properties thereof
- F05D2300/10—Metals, alloys or intermetallic compounds
- F05D2300/14—Noble metals, i.e. Ag, Au, platinum group metals
- F05D2300/143—Platinum group metals, i.e. Os, Ir, Pt, Ru, Rh, Pd
- F05D2300/1435—Rhodium
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2300/00—Materials; Properties thereof
- F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
- F05D2300/603—Composites; e.g. fibre-reinforced
- F05D2300/6033—Ceramic matrix composites [CMC]
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
L’invention concerne un élément (3) de tuyère pour une turbomachine, comportant au moins une partie réalisée en matériau composite à matrice céramique, ladite partie comprenant une surface périphérique (3a), caractérisé en ce qu’au moins une piste (19, 19a, 19b) électriquement conductrice est déposée sur ladite surface périphérique (3a). Figure à publier avec l’abrégé : [Fig. 5]The invention relates to a nozzle element (3) for a turbomachine, comprising at least one part made of ceramic matrix composite material, said part comprising a peripheral surface (3a), characterized in that at least one track (19, 19a, 19b) electrically conductive is deposited on said peripheral surface (3a). Figure to be published with abstract: [Fig. 5]
Description
Domaine technique de l’inventionTechnical field of the invention
L’invention concerne un élément de tuyère pour une turbomachine, telle par exemple qu’un turboréacteur ou un turbopropulseur d’aéronef.The invention relates to a nozzle element for a turbomachine, such as for example a turbojet or an aircraft turboprop.
Etat de la technique antérieureState of the prior art
Un turboréacteur, en particulier du type à double flux, comporte classiquement une soufflante en aval de laquelle s'étend :A turbojet engine, in particular of the turbofan type, conventionally comprises a fan downstream of which extends:
- une veine primaire dans laquelle s'écoule un flux primaire, ladite veine primaire traversant notamment, dans le sens d'écoulement du flux primaire, un compresseur basse-pression, un compresseur haute-pression, une chambre de combustion, une turbine haute-pression et une turbine basse pression,- a primary stream in which a primary stream flows, said primary stream crossing in particular, in the direction of flow of the primary stream, a low-pressure compressor, a high-pressure compressor, a combustion chamber, a high-pressure turbine pressure and a low pressure turbine,
- une veine secondaire, dans laquelle s'écoule un flux secondaire distinct du flux primaire.- a secondary vein, in which flows a secondary flow separate from the primary flow.
La veine secondaire est entourée par une nacelle formant un carénage pour la turbomachine.The secondary vein is surrounded by a nacelle forming a fairing for the turbomachine.
La partie aval du turboréacteur comporte une tuyère d’éjection comportant une partie formant un cône d’éjection, les gaz issus de la veine primaire étant éjectés le long de ladite tuyère d’éjection.The downstream part of the turbojet engine comprises an exhaust nozzle comprising a part forming an exhaust cone, the gases from the primary stream being ejected along said exhaust nozzle.
Les termes amont et aval sont définis par rapport au sens de circulation des gaz au sein de la turbomachine. Les termes axial, radial et circonférentiel sont définis par rapport à l’axe du turboréacteur ou de la turbomachine.The terms upstream and downstream are defined with respect to the direction of circulation of the gases within the turbomachine. The terms axial, radial and circumferential are defined with respect to the axis of the turbojet engine or the turbomachine.
La tuyère d’éjection est généralement formée de plusieurs parties assemblées, l’une au moins des parties étant réalisé dans un matériau composite à matrice céramique ou CMC, afin de limiter la masse de la tuyère tout en offrant une bonne tenue mécanique à des températures élevées.The exhaust nozzle is generally formed of several assembled parts, at least one of the parts being made of a composite material with a ceramic matrix or CMC, in order to limit the mass of the nozzle while offering good mechanical strength at temperatures high.
Cependant, le principal inconvénient d’un matériau CMC est sa très faible conductivité électrique, par exemple de l’ordre de 10E12 ohm.m à température ambiante.However, the main disadvantage of a CMC material is its very low electrical conductivity, for example of the order of 10E12 ohm.m at room temperature.
Il est dès lors difficile de tenir les spécifications de continuité électrique imposées pour l’évacuation des charges électrostatiques ou de la foudre, du fait du caractère isolant d’un tel matériau.It is therefore difficult to meet the electrical continuity specifications imposed for the evacuation of electrostatic charges or lightning, due to the insulating nature of such a material.
L’invention vise à remédier à cet inconvénient de façon simple, fiable et peu onéreuse.The invention aims to remedy this drawback in a simple, reliable and inexpensive manner.
Présentation de l’inventionPresentation of the invention
A cet effet, l’invention concerne un élément de tuyère pour une turbomachine, comportant au moins une partie réalisée en matériau composite à matrice céramique, ladite partie comprenant une surface périphérique, caractérisé en ce qu’au moins une piste électriquement conductrice est déposée sur ladite surface périphérique.To this end, the invention relates to a nozzle element for a turbomachine, comprising at least one part made of ceramic matrix composite material, said part comprising a peripheral surface, characterized in that at least one electrically conductive track is deposited on said peripheral surface.
L’utilisation d’une ou plusieurs pistes conductrices permet d’assurer une continuité électrique de façon à pouvoir assurer l’évacuation des charges électrostatiques ou de la foudre au travers dudit élément.The use of one or more conductive tracks makes it possible to ensure electrical continuity so as to be able to ensure the evacuation of electrostatic charges or lightning through said element.
La piste conductrice peut être réalisée dans un matériau dont la conductivité électrique est inférieure à 10E7 ou 10E8 ohm.m.The conductive track can be made of a material whose electrical conductivity is less than 10E7 or 10E8 ohm.m.
Le matériau de la piste conductrice peut être une encre conductrice.The conductive track material may be a conductive ink.
Ladite encre conductrice peut comporter des microparticules ou nanoparticules métalliques, par exemple à base Ag, CuNiMn, Pt, Ti , NiCr ou PtRh.Said conductive ink may comprise metallic microparticles or nanoparticles, for example based on Ag, CuNiMn, Pt, Ti, NiCr or PtRh.
La piste conductrice peut présenter une épaisseur comprise entre 1 et 30 microns.The conductive track can have a thickness of between 1 and 30 microns.
La piste conductrice peut présenter une largeur comprise entre 0,5 et 7 mm.The conductive track may have a width of between 0.5 and 7 mm.
Ainsi la section de la piste conductrice peut être comprise entre 0,05 et 1 mm².Thus the section of the conductive track can be between 0.05 and 1 mm².
La piste conductrice peut s’étendre selon une trajectoire dont au moins une portion est courbe.The conductive track can extend along a trajectory of which at least a portion is curved.
La courbure de ladite portion de la piste conductrice permet de créer une souplesse capable de compenser d’éventuels effets de dilatation différentielle entre la piste conductrice et son support, à savoir la partie en CMC.The curvature of said portion of the conductive track makes it possible to create flexibility capable of compensating for any effects of differential expansion between the conductive track and its support, namely the CMC part.
L’élément peut comporter plusieurs pistes conductrices. Au moins deux pistes peuvent se croiser. Au moins deux pistes peuvent être parallèles l’une à l’autre. Au moins une piste peut s’étendre dans la direction axiale ou peut s’étendre en formant un angle avec la direction axiale.The element may comprise several conductive tracks. At least two tracks can intersect. At least two tracks can be parallel to each other. At least one track may extend in the axial direction or may extend at an angle to the axial direction.
L’élément peut être annulaire et s’étendre selon un axe qui est confondu avec l’axe de la tuyère et de la turbomachine. Au moins une piste conductrice peut s’étendre circonférentiellement. Au moins une piste conductrice peut s’étendre sous la forme d’une hélice.The element may be annular and extend along an axis which coincides with the axis of the nozzle and of the turbomachine. At least one conductive track may extend circumferentially. At least one conductive track may extend in the form of a helix.
La piste conductrice peut être formée sur une surface annulaire radialement externe ou sur une surface annulaire radialement interne de l’élément.The conductive track can be formed on a radially outer annular surface or on a radially inner annular surface of the element.
La piste conductrice peut être recouverte, au moins en partie, par une couche de protection. Ladite couche de protection peut être réalisée avec des matériaux de type verre ou vitrocéramique. L’épaisseur de la couche de protection peut être comprise entre 0,03 et 0,1 mm. Ladite couche de protection peut être déposée par un procédé de type sérigraphie, spray ou projection plasma.The conductive track may be covered, at least in part, by a protective layer. Said protective layer can be produced with materials of the glass or glass-ceramic type. The thickness of the protective layer can be between 0.03 and 0.1 mm. Said protective layer can be deposited by a process of the screen printing, spray or plasma projection type.
L’invention concerne également un ensemble comportant au moins un premier élément et au moins un second élément comme plus haut, caractérisé en ce que la piste du premier élément est connectée électriquement avec la piste du second élément.The invention also relates to an assembly comprising at least a first element and at least a second element as above, characterized in that the track of the first element is electrically connected with the track of the second element.
On assure ainsi la connexion électrique d’un élément à l’autre de l’ensemble, de façon à permettre l’évacuation des charges électriques au travers des différents éléments successifs de l’ensemble.This ensures the electrical connection from one element to another of the assembly, so as to allow the evacuation of electrical charges through the various successive elements of the assembly.
Le premier élément et le second élément peuvent être reliés mécaniquement l’un à l’autre par au moins un organe de liaison mécanique qui est électriquement conducteur, la piste du premier élément étant en contact avec une première partie de l’organe de liaison, la piste du second élément étant en contact avec une seconde partie de l’organe de liaison.The first element and the second element can be mechanically connected to each other by at least one mechanical connection member which is electrically conductive, the track of the first element being in contact with a first part of the connection member, the track of the second element being in contact with a second part of the connecting member.
De cette manière, la liaison électrique entre les deux pistes peut être réalisée par l’intermédiaire de l’organe de liaison.In this way, the electrical connection between the two tracks can be made via the connecting device.
L’organe de liaison peut être amovible. L’organe de liaison peut être un boulon ou un rivet.The connecting member may be removable. The connecting member can be a bolt or a rivet.
La première partie de l’organe de liaison être une tête de vis. La seconde partie de l’organe de liaison peut être la tige de la vis ou l’écrou.The first part of the connecting member will be a screw head. The second part of the connecting member can be the shank of the screw or the nut.
Le premier élément peut comporter un lamage ou une empreinte au niveau de laquelle s’étend la piste conductrice du premier élément, la tête de vis venant en appui sur la piste conductrice, au niveau de ladite empreinte ou dudit lamage.The first element may comprise a counterbore or an indentation at the level of which the conductive track of the first element extends, the screw head bearing on the conductive track, at the level of said indentation or of said counterbore.
L’extrémité aval du premier élément peut être située radialement à l’intérieur de l’extrémité amont du second élément. Les pistes du premier élément peuvent être déposées sur la surface radialement externe du premier élément. Les pistes du second élément peuvent être déposées sur la surface radialement externe du second élément. Les pistes du premier élément peuvent traverser l’épaisseur du premier élément de façon à venir en contact avec les pistes du second élément.The downstream end of the first element can be located radially inside the upstream end of the second element. The tracks of the first element can be deposited on the radially outer surface of the first element. The tracks of the second element can be deposited on the radially outer surface of the second element. The tracks of the first element can pass through the thickness of the first element so as to come into contact with the tracks of the second element.
Le premier élément peut être un cône d’une tuyère. Le second élément peut être une virole apte à délimiter un caisson acoustique, monté en amont du premier élément.The first element can be a nozzle cone. The second element can be a ferrule capable of delimiting an acoustic box, mounted upstream of the first element.
L’invention peut également concerner une tuyère comportant au moins un élément du type précité ou au moins un ensemble du type précité.The invention may also relate to a nozzle comprising at least one element of the aforementioned type or at least one assembly of the aforementioned type.
L’invention peut également concerne une turbomachine, par exemple un turboréacteur ou un turbopropulseur d’aéronef, comportant au moins un élément du type précité ou un ensemble du type précité. L’aéronef peut être un avion.The invention may also relate to a turbomachine, for example a turbojet or an aircraft turboprop, comprising at least one element of the aforementioned type or an assembly of the aforementioned type. The aircraft may be an airplane.
L’invention concerne également un procédé de fabrication d’un élément selon l’une des revendications 1 à 7, caractérisé en ce que la piste conductrice est formée par dépôt d’une encre conductrice.The invention also relates to a method of manufacturing an element according to one of Claims 1 to 7, characterized in that the conductive track is formed by depositing a conductive ink.
Le dépôt d’encre conductrice est par exemple réalisé par jet d’encre, par un procédé de type aerosol jet printing ou AJP, sérigraphie, dispensing ou microdispensing ou fusion laser.The deposition of conductive ink is for example carried out by inkjet, by a process of the aerosol jet printing or AJP type, screen printing, dispensing or microdispensing or laser fusion.
L’encre conductrice est par exemple une suspension, typiquement contenant au moins un solvant, au moins un liant organique et des micro- ou nanoparticules métalliques, par exemple à base Ag, CuNiMn, Pt, Ti, NiCr ou PtRh.The conductive ink is for example a suspension, typically containing at least one solvent, at least one organic binder and metallic micro- or nanoparticles, for example based on Ag, CuNiMn, Pt, Ti, NiCr or PtRh.
Les particules à base de CuNiMn, Pt ou PtRh sont notamment utilisées pour des applications au-delà de 600°C, le point de fusion de l’argent étant situé aux alentours de 600°C.Particles based on CuNiMn, Pt or PtRh are used in particular for applications above 600°C, the melting point of silver being around 600°C.
Brève description des figuresBrief description of figures
Claims (8)
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| FR2112225A FR3129181B1 (en) | 2021-11-18 | 2021-11-18 | Nozzle element for a turbomachine |
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| FR2112225A FR3129181B1 (en) | 2021-11-18 | 2021-11-18 | Nozzle element for a turbomachine |
| FR2112225 | 2021-11-18 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| FR3129181A1 true FR3129181A1 (en) | 2023-05-19 |
| FR3129181B1 FR3129181B1 (en) | 2024-04-19 |
Family
ID=80999707
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| FR2112225A Active FR3129181B1 (en) | 2021-11-18 | 2021-11-18 | Nozzle element for a turbomachine |
Country Status (1)
| Country | Link |
|---|---|
| FR (1) | FR3129181B1 (en) |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP2834150B1 (en) * | 2012-04-06 | 2016-05-04 | Herakles | Device providing protection against lightning |
| EP3226664A2 (en) * | 2016-03-31 | 2017-10-04 | The Boeing Company | Electrical conductor pathway system and method of making the same |
| FR3084917A1 (en) * | 2018-08-09 | 2020-02-14 | Safran Ceramics | ASSEMBLY FOR A TURBOMACHINE EJECTION NOZZLE |
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2021
- 2021-11-18 FR FR2112225A patent/FR3129181B1/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP2834150B1 (en) * | 2012-04-06 | 2016-05-04 | Herakles | Device providing protection against lightning |
| EP3226664A2 (en) * | 2016-03-31 | 2017-10-04 | The Boeing Company | Electrical conductor pathway system and method of making the same |
| FR3084917A1 (en) * | 2018-08-09 | 2020-02-14 | Safran Ceramics | ASSEMBLY FOR A TURBOMACHINE EJECTION NOZZLE |
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| Publication number | Publication date |
|---|---|
| FR3129181B1 (en) | 2024-04-19 |
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